Method and apparatus for aerodynamic flow control using compact high-frequency fluidic actuator arrays

• US 8,382,043 B1
• Filed: 07/16/2010
• Issued: 02/26/2013
• Est. Priority Date: 08/17/2009
• Status: Active Grant

• Current Assignee: Surya Raghu
• Original Assignee: Surya Raghu
• Inventors: Raghu, Surya
• Primary Examiner(s): Dinh, Tien
• Assistant Examiner(s): Green, Richard R
• Application Number:
  US12/804,225
• Time in Patent Office: 956 Days
• Field of Search: 244/1.N, 244/200, 244/200.1, 244/204, 244/204.1, 244/207, 244/208, 244/209
• US Class Current: 244/207
• CPC Class Codes: B64C 21/04 for blowing
• CPC Class Codes: B64C 2230/04 by actively generating fluid flow
• CPC Class Codes: B64C 2230/18 by using small jets that make the fluid flow oscillate
• CPC Class Codes: F15D 1/008 comprising fluid injection or suction means
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

The present invention is directed to the manufacture of and the use of an aerodynamic flow control device having a compact array of a plurality of fluidic actuators in planar, curved, circular and annular configurations. The compact array of fluidic actuators of the invention may be designed to produce oscillating or pulsed jets at the exit ports with frequencies in the range of 1-22 kHz. They may be integrally manufactured along with the wing sections, flaps, tail and rudder of airplane, the inlet or exit geometries of a jet engine. When supplied with a source of fluid such as air, these arrays of actuators produce a set of fluid jets of random phase of high velocity and influence the main stream of air over the subject surface. The beneficial effects of modifying flow using the present invention include increased lift, reduced drag, improved performance and noise reduction in jet engines.

Claims

1. An aerodynamic flow control device comprising a compact arrangement of an array of a plurality of discrete fluidic actuators having non-interconnected feedback channels located on a substrate wherein each of said plurality of said fluidic actuators comprises an input port and an exit port wherein each of said actuators is capable of producing at said exit port an oscillating or sweeping jet either in-plane or perpendicular to the plane of the fluid flow inside said actuator further comprising a common extension chamber extending from the exit ports of said plurality of fluidic actuators thereby directing the exiting flow in a specific or predetermined direction.

2. The aerodynamic flow control device of claim 1 wherein said compact arrangement of the array is in a flat plane structure, a non-planar surface or in an annular geometry.

3. The aerodynamic flow control device of claim 1 wherein said exit ports of said fluidic actuators are in a single plane or in a staggered configuration.

4. The aerodynamic flow control device of claim 1 wherein said compact arrangement of said array of said plurality of fluidic actuators are multilayered or in multiple rows.

5. The aerodynamic flow control device of claim 1 further comprising a plenum chamber commonly connected to each of said plurality of discrete fluidic actuators.

6. The aerodynamic flow control device of claim 1 wherein said compact array of a plurality of fluidic actuators is present on both sides of said substrate.

7. An aerodynamic flow control device comprising a compact composite comprising a compact array of a plurality of discrete fluidic actuators having non-interconnected feedback channels located on a substrate wherein each of said fluidic actuators comprises an input port and an exit port and wherein each of said fluidic actuators is capable of producing oscillating or sweeping jets at said exit port, a plenum chamber commonly connected to each of said plurality of fluidic actuators, a cover plate attached to said compact array of fluidic actuators and said plenum chamber and further comprising a common extension chamber extending from the exit ports of said plurality of fluidic actuators thereby directing the exiting flow in a specific or predetermined direction.

8. The aerodynamic flow control device of claim 7 wherein a fluid is supplied to the plenum chamber by means of a connector integrally attached to the said cover plate.

9. The aerodynamic flow control device of claim 7 wherein said plenum chamber is selected from being integral to said array or being externally connected to said array.

10. The aerodynamic flow control device of claim 7 wherein said extension chamber is either an integrally built component or is an attachment to said compact composite of said fluidic array.

11. The aerodynamic flow control device of claim 7 wherein said compact composite is selected from planar, non-planar or annular geometric structures.

12. A method of flow control or noise reduction in an aerodynamic device comprising the steps of providing a compact array of a plurality of discrete fluidic actuators having non-interconnected feedback channels located on a substrate wherein each of said fluidic actuators comprises an input port, an exit port and a common extension chamber extending from the exit ports of said plurality of fluidic actuators to direct the exiting flow in a specific or predetermined direction, introducing fluid at the said input port of said plurality of fluidic actuators and thereby producing at said exit ports of said plurality of fluidic actuators oscillating or sweeping fluid jets either in-plane or perpendicular to the plane of the fluid flow inside said actuators a resultant flow control or noise reduction in said aerodynamic device.